Volume 25, Issue 1 (January 2024)
Modares Mechanical Engineering 2024, 25(1): 1-9 |
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Optimization of CDA airfoil Geometry of a transonic Axial Compressor, using Genetic Algorithm And CFD. Modares Mechanical Engineering 2024; 25 (1) :1-9
URL: http://mme.modares.ac.ir/article-15-74512-en.html
URL: http://mme.modares.ac.ir/article-15-74512-en.html
Abstract: (463 Views)
In recent years, due to the optimal geometry and lower pressure drop, diffusion control vanes have significant applications, especially in the aviation industry and in subsonic and transsonic conditions. In the current research, the airfoil of the axial stator compressor section designed in the National Aerospace Laboratory of India has been selected as the basic geometry. The goal of optimization is to minimize the pressure drop of the entire fluid flow and consequently reduce the drop rate. The working method in this research is the change in the profile geometry of the blade by changing the parameters of the parsec method, which leads to the creation of new geometries at each stage of the code execution. The used optimization method is developed based on Genetic Algorithm. For the aerodynamic analysis of the generated geometry in each step and extracting the total pressure drop value, the MATLAB code is coupled with Ansys software and in each step, after numerical solution for each generated geometry, the total pressure drop value is extracted and returned to the code. Finally, the work output of the vane is more optimal and with a lower pressure drop, which is finally compared with the original vane and introduced as a suitable alternative. The total pressure drop between inlet and outlet in the optimized vane has decreased by 18% compared to the original vane, and the mass flow rate has also increased by 0.083 kg/s, which is a significant amount. The improvement of various aerodynamic characteristics such as Mach number distribution and pressure and drop coefficients can also be seen between the two basic and optimized blades, which is detailed at the end of the article
Keywords: Controlled Diffusion Airfoil, Geometry Optimization, Axial Compressor, PARSEC Method, Genetic Algorithm
Article Type: Original Research |
Subject:
Gas Turbine
Received: 2024/04/1 | Accepted: 2025/01/31 | Published: 2024/12/30
Received: 2024/04/1 | Accepted: 2025/01/31 | Published: 2024/12/30
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